Lycoming TEO-540-C1A Maintenance Manual page 456

Fault ID 116
Fault
CAN 2 error fault
Description
Root Cause This fault indicates a hardware error detected in CAN 2 device
1. Is the fault intermittent? If yes, see note. If no, go to step 2.
2. With ignition switch in OFF position, remove ECU power by pulling the ECU circuit breaker. Wait 10s
before resetting. Is fault still active? If yes, go to step 3.
3. Disconnect each hardware item connected to the CAN bus, one at a time (ie. Data logger...etc.). Is fault
still active? If yes, go to step 4. If no, replace the hardware item that caused the fault.
4. Complete a continuity and short circuit test of the harness from the aircraft CAN interface connector to
ECU connectors using the engine system schematic and aircraft wiring diagram. If the continuity or
short circuit check fails, isolate to affected harness by disconnecting the airframe interface connection
AF-P1. If problem is isolated to engine airframe harness, contact Lycoming Engines. If problem is
found from CAN interface connector to AF-J1, repair in accordance with aircraft maintenance manual.
If the continuity check is good, replace the ECU.
NOTE: If this fault is intermittent, it is due to too much data being requested from the ECU than the
controller can provide through CAN 2. This fault, if it is intermittent, does not affect the operation or
performance of the system, and is considered low risk.
Fault ID 117
Fault
CAN 3 error fault
Description
Root Cause This fault indicates a hardware error detected in CAN 3 device
1. Is the fault intermittent? If yes, see note. If no, go to step 2.
2. With Ignition switch in OFF position, remove ECU power by pulling the ECU circuit breaker. Wait 10s
before resetting. Is fault still active? If yes, go to step 3.
3. Disconnect each hardware item connected to the CAN bus, one at a time (ie. Engine instrument
display...etc.). Is fault still active? If yes, go to step 4. If no, replace the hardware item that caused the
fault.
4. Disconnect connector(s) from aircraft engine instrumentation display. Did fault go inactive? If yes,
isolate fault in engine instrumentation display system. If no, go to step 5.
5. Complete a continuity and short circuit test of the harness from the aircraft engine instrument display
connector to ECU connector using the engine system schematic and aircraft wiring diagram. If the
continuity or short circuit check fails, isolate to affected harness by disconnecting the airframe interface
connection AF-P1. If problem is isolated to engine airframe harness, contact Lycoming Engines. If
problem is found from aircraft engine instrument display connector to AF-J1, repair in accordance with
aircraft maintenance manual. If the continuity check is good, using aircraft maintenance manual, and
serviceability of the aircraft engine instrument display has been verified, replace the ECU.
NOTE: If this fault is intermittent, it is due to too much data being requested from the ECU than the
controller can provide through CAN 3. This fault, if it is intermittent, does not affect the operation or
performance of the system, and is considered low risk.
Appendix D
Page 426
Fault Group 15
Troubleshooting Steps
Fault Group 15
Troubleshooting Steps
TEO-540-C1A Engine Maintenance Manual
Fault Name
[FAULT: CAN2 Error]
Fault Lamp
Fault Name
[FAULT: CAN3 Error]
Fault Lamp
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November 2018